Icing condition detection system

ABSTRACT

A method and apparatus for detecting an icing condition. The apparatus comprises a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

BACKGROUND INFORMATION

1. Field

The present disclosure relates generally to aircraft and, in particular,to detecting icing conditions for an aircraft. Still more particularly,the present disclosure relates to a method and apparatus for detectingice on the surface of an aircraft.

2. Background

In aviation, icing conditions in the atmosphere may lead to theformation of ice on the surfaces of the aircraft. Further, this ice alsomay occur within the engine. Ice forming on the surfaces of theaircraft, on the inlets of an engine, and other locations is undesirableand potentially unsafe for operating the aircraft.

Icing conditions may occur when drops of supercooled liquid water arepresent. In these illustrative examples, water is considered to besupercooled when the water is cooled below the stated freezing point forwater but is still in a liquid form. Icing conditions may becharacterized by the size of the drops, the liquid water content, theair temperature, and other suitable parameters. These parameters mayaffect the rate and extent at which ice forms on an aircraft.

When icing occurs, the aircraft does not operate as desired. Forexample, ice on the wing of an aircraft will cause the aircraft to stallat a lower angle of attack and have an increased level of drag.

Aircraft may have mechanisms to prevent icing, remove ice, or somecombination thereof to handle these icing conditions. For example,aircraft may include icing detection, prevention, and removal systems.Ice may be removed using deicing fluid, infrared heating, and othersuitable mechanisms.

With respect to detecting ice on the surface of an aircraft, icedetection systems that are currently available may not detect formationof ice on the surface of an aircraft as accurately as desired. Withcurrently used ice detection systems, false indications of ice mayoccur.

For example, one ice detection system detects moisture and temperature.If moisture is present in the environment around the aircraft and if thetemperature is low enough, then the ice detection system indicates thatice is present on the surface of the aircraft. However, in some cases,ice may not actually be present on the surface of that aircraft.Depending on the conditions in the environment, moisture may not formice until temperatures that are lower than the temperatures used as athreshold to indicate a presence of ice are present. Thus, inaccurateindication of a presence of ice may occur.

Further, both small and large supercooled droplets may accumulate on thesurface of the aircraft. The accumulation of each type of supercooleddroplet may require different safety considerations. For example, whenlarge supercooled droplets accumulate on the aircraft, those dropletsmay become a safety concern for the safe flight of the aircraft. Withsmall supercooled droplets, those droplets may accumulate on the forwardedges of the aircraft without becoming as much of a safety concern tothe flight of the aircraft. Current ice detection systems may notdifferentiate between small and large supercooled droplets. Thus,inaccurate information about the type and severity of ice may occur.

Therefore, it would be desirable to have a method and apparatus thattakes into account at least some of the issues discussed above, as wellas other possible issues.

SUMMARY

In one illustrative embodiment, an apparatus comprises a piezoelectricmaterial and a vibration detector. The piezoelectric material has asurface proximate to a surface of a vehicle. The piezoelectric materialis configured to vibrate. The vibration detector is configured to detecta change in vibrations in the piezoelectric material that indicates apresence of an icing condition on the surface of the piezoelectricmaterial.

In another illustrative embodiment, a method for detecting whether anicing condition is present is provided. Vibrations are caused in apiezoelectric material associated with a surface of a vehicle. Adetermination is made as to whether the icing condition is present on asurface of the piezoelectric material from the vibrations.

The features and functions can be achieved independently in variousembodiments of the present disclosure or may be combined in yet otherembodiments in which further details can be seen with reference to thefollowing description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

The novel features believed characteristic of the illustrativeembodiments are set forth in the appended claims. The illustrativeembodiments, however, as well as a preferred mode of use, furtherobjectives and features thereof, will best be understood by reference tothe following detailed description of an illustrative embodiment of thepresent disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 is an illustration of an aircraft in accordance with anillustrative embodiment;

FIG. 2 is an illustration of a block diagram of an icing conditiondetection environment in accordance with an illustrative embodiment;

FIG. 3 is an illustration of a block diagram of a piezoelectric sensorin accordance with an illustrative embodiment;

FIG. 4 is an illustration of a block diagram of a data packet that maybe generated by a piezoelectric sensor in accordance with anillustrative embodiment;

FIG. 5 is an illustration of a piezoelectric sensor in accordance withan illustrative embodiment;

FIG. 6 is an illustration of a cross-sectional view of a piezoelectricsensor installed in an aircraft fuselage in accordance with anillustrative embodiment;

FIG. 7 is an illustration of a flowchart of a process for detecting anicing condition in accordance with an illustrative embodiment;

FIG. 8 is an illustration of a flowchart of a process for detectingvibrations in a piezoelectric sensor in accordance with an illustrativeembodiment;

FIG. 9 is an illustration of a flowchart of a process for determiningwhether an icing condition is present in accordance with an illustrativeembodiment;

FIG. 10 is an illustration of a data processing system in accordancewith an illustrative embodiment;

FIG. 11 is an illustration of an aircraft manufacturing and servicemethod in accordance with an illustrative embodiment; and

FIG. 12 is an illustration of an aircraft in which an illustrativeembodiment may be implemented.

DETAILED DESCRIPTION

The illustrative embodiments recognize and take into account a number ofdifferent considerations. For example, the illustrative embodimentsrecognize and take into account that rather than detecting a presence ofmoisture and the temperature in the environment around an aircraft,detecting the actual presence of ice or liquid on the surface of theaircraft may increase the accuracy at which ice or liquid is detected onan aircraft.

For example, the illustrative embodiments recognize and take intoaccount that using a sensor with a surface that vibrates may provide amore accurate indication of a presence of an icing condition. Forexample, the vibrations may change differently when water or ice ispresent on the surface of the sensor.

With reference now to the figures and, in particular, with reference toFIG. 1, an illustration of an aircraft is depicted in accordance with anillustrative embodiment. In this illustrative example, aircraft 100 haswing 102 and wing 104 attached to fuselage 106. Aircraft 100 alsoincludes engine 108 attached to wing 102 and engine 110 attached to wing104.

Fuselage 106 has nose section 112 and tail section 114. Nose section 112is the forward part of aircraft 100, while tail section 114 is the aftpart of aircraft 100. Horizontal stabilizer 116, horizontal stabilizer118, and vertical stabilizer 120 are attached to tail section 114 offuselage 106.

Aircraft 100 is an example of an aircraft in which icing conditiondetection system 122 may be implemented in accordance with anillustrative embodiment. In these illustrative examples, icing conditiondetection system 122 comprises sensors 124 on surface 126 of aircraft100.

In these illustrative examples, a sensor in sensors 124 may include apiezoelectric material. The piezoelectric material has a surfaceproximate to surface 126 of aircraft 100 and is configured to vibrate.When ice forms on the surface of the piezoelectric material, thevibrations in the piezoelectric material change. The change invibrations in the piezoelectric material may be detected to determinewhether ice is present on the surface of the piezoelectric material.Additionally, an amount of ice that is built up on the surface of thepiezoelectric material also may be identified through the changes in thevibrations of the piezoelectric material over time.

In these illustrative examples, sensors 124 in icing condition detectionsystem 122 may be located in different locations on surface 126 ofaircraft 100. As depicted, sensors 124 comprise sensors 130, 132, 134,136, 137, 138, 139, 140, 141, 142, 143, 144, 146, and 148.

In these illustrative examples, sensors 130, 132, and 134 are located onfuselage 106 of aircraft 100. In this illustrative example, sensor 130is located on top side 150 of fuselage 106. Sensor 132 is located onside 152 of fuselage 106, while sensor 134 is located on side 154 offuselage 106. Side 152 and side 154 are opposite of each other onfuselage 106. In this illustrative example, sensor 134 is shown inphantom on side 154 of fuselage 106.

In these illustrative examples, sensors 130, 132, and 134 are located ator above horizontal center line 156 in fuselage 106. Due to the relativeposition of these sensors, sensors 130, 132, and 134 may be in locationsthat avoid or reduce exposure to runway debris when aircraft 100 taxison a runway.

Sensor 136 and sensor 138 are located on the engine housings of engine108 and engine 110, respectively. Sensors 137, 139, and 140 are locatedon wing 102, while sensors 141, 142, and 143 are located on wing 104.Sensor 146 is located on horizontal stabilizer 116, and sensor 144 islocated on horizontal stabilizer 118. Sensor 148 is located on verticalstabilizer 120.

The illustration of sensors 124 is not meant to imply physical orarchitectural limitations to the manner in which sensors may be locatedon aircraft 100 or other aircraft. In these illustrative examples,although 14 sensors are illustrated for sensors 124, other numbers ofsensors may be implemented. For example, only a single sensor may bepresent in icing condition detection system 122 instead of a number ofsensors 124. As used herein, a “number of” when used with reference toitems means one or more items. In other words, number of sensors 124 isone or more sensors.

The distribution of sensors 124 on surface 126 of aircraft 100 may allowicing condition detection system 122 to detect different types of icingdistribution on portions of surface 126 of aircraft 100. For example,icing conditions on wing 102 of aircraft 100 may be different atdifferent portions of wing 102. As an example, droplets of ice mayaccumulate more densely at sensor 137 than at sensor 140. As a result,icing condition detection system 122 may be used to determine whether aconcern is present for the safe flight of aircraft 100, depending on thedistribution of ice on wing 102 or other portions of aircraft 100.

Icing condition detection system 122 also may detect icing conditionsbefore ice forms. For example, icing condition detection system 122 maydetect water droplets in conditions where the water droplets may formice. In other words, the icing condition may be at least one of ice onthe surface and water droplets on the surface in conditions that causewater droplets to form ice.

As used herein, the phrase “at least one of”, when used with a list ofitems, means different combinations of one or more of the listed itemsmay be used and only one of each item in the list may be needed. Forexample, “at least one of item A, item B, and item C” may include,without limitation, item A or item A and item B. This example also mayinclude item A, item B, and item C, or item B and item C.

Turning next to FIG. 2, an illustration of a block diagram of an icedetection environment is depicted in accordance with an illustrativeembodiment. Icing condition detection environment 200 is an environmentin which ice detection may be performed for vehicle 202. In thisillustrative example, vehicle 202 may be aircraft 100 in FIG. 1.

Icing condition detection system 204 may be associated with vehicle 202.When one component is “associated” with another component, theassociation is a physical association in these depicted examples. Forexample, a first component, icing condition detection system 204, may beconsidered to be associated with a second component, vehicle 202, bybeing secured to the second component, bonded to the second component,mounted to the second component, welded to the second component,fastened to the second component, and/or connected to the secondcomponent in some other suitable manner. The first component also may beconnected to the second component using a third component. The firstcomponent may also be considered to be associated with the secondcomponent by being formed as part of and/or an extension of the secondcomponent.

In these illustrative examples, icing condition detection system 204takes the form of piezoelectric icing condition detection system 206.Piezoelectric icing condition detection system 206 includes number ofpiezoelectric sensors 208. As depicted, number of piezoelectric sensors208 may be located substantially flush or planar to surface 210 ofvehicle 202.

In these illustrative examples, number of piezoelectric sensors 208generates vibrations 212. Vibrations 212 may be used to determinewhether ice 224 is present on surface 210 of vehicle 202.

Piezoelectric icing condition detection system 206 also includesvibration generation system 214, vibration detection system 216, andcontroller 218. Vibration generation system 214 is hardware configuredto generate electrical signals that cause number of piezoelectricsensors 208 to generate vibrations 212.

In these illustrative examples, vibrations 212 have shear mode 220.Vibrations 212 having shear mode 220 involve waves that have motion in adirection that is substantially perpendicular to the direction in whichthe waves propagate.

Vibration detection system 216 is configured to detect vibrations 212.In particular, vibration detection system 216 may detect the frequencyof vibrations 212. Vibration detection system 216 is configured togenerate data 222. In these illustrative examples, data 222 may be, forexample, without limitation, at least one of a frequency distribution,amplitude, relative phase of vibrations in vibrations 212 with respectto other vibrations in vibrations 212, or some other suitable parameter.Also, multiple vibrations with different frequencies may be present anddetected from data 222.

Data 222 is used by controller 218 to determine whether ice 224 ispresent on surface 210 of vehicle 202. Controller 218 may be implementedin hardware, software, or a combination of the two. In theseillustrative examples, controller 218 may be implemented within computersystem 226. Computer system 226 is one or more computers. When more thanone computer is present in computer system 226, those computers may bein communication with each other using a communications medium such as anetwork.

When software is used, the operations performed by the components may beimplemented in program code configured to be run on a processor unit.When hardware is employed, the hardware may include circuits thatoperate to perform the operations in the components.

In these illustrative examples, the hardware may take the form of acircuit system, an integrated circuit, an application specificintegrated circuit (ASIC), a programmable logic device, or some othersuitable type of hardware configured to perform a number of operations.With a programmable logic device, the device is configured to performthe number of operations. The device may be reconfigured at a later timeor may be permanently configured to perform the number of operations.Examples of programmable logic devices include, for example, aprogrammable logic array, a programmable array logic, a fieldprogrammable logic array, a field programmable gate array, and othersuitable hardware devices. Additionally, the processes may beimplemented in organic components integrated with inorganic componentsand/or may be comprised entirely of organic components excluding a humanbeing. For example, the processes may be implemented as circuits inorganic semiconductors.

Controller 218 analyzes data 222 to determine whether vibrations 212 atany of number of piezoelectric sensors 208 indicate a presence of ice224 on surface 210 of vehicle 202. Further, controller 218 also maydetermine a mass of ice 224 detected on surface 210 of vehicle 202.

In response to detecting a presence of ice 224 on surface 210 of vehicle202, operation 228 may be performed by controller 218. Operation 228 maytake a number of different forms. For example, operation 228 may be atleast one of generating an alert indicating a presence of ice 224,initiating operation of anti-icing system 230, and other suitableoperations.

In these illustrative examples, the alert may include a visualindicator, a sound, or other suitable alert that may be presented to theoperator of vehicle 202. In some cases, the alert also may be sent to anoperator or computer system in a location remote to vehicle 202.

Anti-icing system 230 is configured to remove ice 224 from surface 210of vehicle 202. Additionally, anti-icing system 230 also may beconfigured to remove ice from number of piezoelectric sensors 208.Anti-icing system 230 may take a number of different forms. For example,without limitation, anti-icing system 230 may be selected from at leastone of an infrared heater, an electrical resistive heater, a de-icerboot, and other suitable types of anti-icing devices.

Further, icing condition detection system 204 may also detect conditionson surface 210 where ice 224 may form before ice 224 forms on surface210 of vehicle 202. For example, number of piezoelectric sensors 208 inicing condition detection system 204 may detect water droplets 232 thatreach number of piezoelectric sensors 208 on surface 210 of vehicle 202in conditions where ice 224 may form. The detection of ice 224, waterdroplets 232, or both ice 224 and water droplets 232 may be used toidentify one or more types of icing conditions that may be present. Inother words, an icing condition may be present when ice 224 has formedon surface 210, when water droplets 232 are detected on surface 210 whenthe environmental conditions may cause water droplets 232 to form ice224, or both.

Turning now to FIG. 3, an illustration of a block diagram of apiezoelectric sensor is depicted in accordance with an illustrativeembodiment. Piezoelectric sensor 300 is an example of a sensor in numberof piezoelectric sensors 208 in FIG. 2.

As depicted, piezoelectric sensor 300 includes housing 302,piezoelectric material 304, piezoelectric material 305, vibrationgenerator 306, temperature sensor 307, vibration detector 308, andheater 309. In these illustrative examples, piezoelectric material 304,piezoelectric material 305, vibration generator 306, temperature sensor307, vibration detector 308, and heater 309 are associated with housing302. Temperature sensor 307 may be used to monitor the temperature ofpiezoelectric material 304.

Housing 302 is a structure configured to be mounted in vehicle 202. Inparticular, housing 302 may be configured to be mounted substantiallyflush or planar to surface 210 of vehicle 202. When housing 302 ismounted substantially flush to surface 210 of vehicle 202, housing 302and the different components associated with housing 302 may not add tothe drag on vehicle 202 when vehicle 202 is moving.

Piezoelectric material 304 is a material in which an electricalmechanical interaction is present between the electrical state and themechanical state. In these illustrative examples, piezoelectric material304 takes the form of crystals 310. Piezoelectric material 304 isconfigured to vibrate when an electrical charge is applied topiezoelectric material 304 in these illustrative examples.

Piezoelectric material 305 may take the form of crystals 311. In theseillustrative examples, piezoelectric material 305 is selected to besubstantially identical to piezoelectric material 304. In other words,piezoelectric material 304 and piezoelectric material 305 may beselected to be the same material and have substantially the samedimensions.

Piezoelectric material 304 and piezoelectric material 305 may beselected from a number of different materials. For example, withoutlimitation, piezoelectric material 304 and piezoelectric material 305may be selected from one of a piezoelectric crystal, a piezoelectricceramic, quartz, gallium phosphate, and other suitable materials.

Vibration generator 306 is hardware and also may include software. Inthis illustrative example, vibration generator 306 is an example of adevice that may be implemented in vibration generation system 214 inFIG. 2.

As depicted, vibration generator 306 is electrically connected topiezoelectric material 304 and piezoelectric material 305. Vibrationgenerator 306 is configured to cause vibrations 312 in piezoelectricmaterial 304 and vibrations 313 in piezoelectric material 305.

In this illustrative example, vibrations 312 have shear mode 314.Additionally, vibrations 313 may have shear mode 315. Vibrations 312having shear mode 314 and vibrations 313 having shear mode 315 involvewaves that have motion in a direction that is substantiallyperpendicular to the direction in which the waves propagate.

In these illustrative examples, piezoelectric material 304 andpiezoelectric material 305 may react differently to different types ofconditions. For example, piezoelectric material 304 and piezoelectricmaterial 305 may be less disturbed by liquid droplets than bysupercooled droplets. In other words, vibrations 212 having shear mode314 and vibrations 313 having shear mode 315 may not occur for liquiddroplets in the same manner as with supercooled droplets. As a result,piezoelectric sensor 300 may be able to distinguish between liquidloading and ice loading on the surface of the piezoelectric material.

As depicted, the presence of the two types of water droplets mayindicate different types of icing conditions. For example, a first typeof icing condition and a second type of icing condition may be caused bydrops of water of different sizes. Although the altitude, temperature,and liquid water content ranges may be the same, one difference betweenthe first and second types of icing conditions is the drop size.

In these illustrative examples, these icing conditions may occur atdifferent altitudes and temperatures that cause the formation of ice onvehicle 202 when vehicle 202 takes the form of aircraft 100. Forexample, icing conditions may be present at an altitude from about sealevel to about 30,000 feet when the temperature is from about −40degrees Celsius to about zero degrees Celsius. Of course, otheraltitudes and temperatures may be present at which ice may be formedfrom water that contacts surface 126 of aircraft 100. Icing conditionsalso may be present when the liquid water content in the drops is fromabout 0.4 to about 2.8 grams/cubic meter at the altitude and temperaturerange described above.

In these illustrative examples, the first type of icing condition may bepresent when the size of the drops is from about 0.00465 millimeters indiameter to about 0.111 millimeters in diameter. Drops with these sizesmay be referred to as normal drops. The second type of icing conditionmay be present when the size of the drops includes drops that have adiameter greater than about 0.111 millimeters. Drops having a sizegreater than about 0.111 millimeters may be referred to as large dropsand, in particular, may be called supercooled large drops under selectedaltitude, temperature, and liquid water content conditions. Water isconsidered to be supercooled when the water is cooled below the statedfreezing point for water but is still in a liquid form.

As depicted, piezoelectric sensor 300 may be configured to detect iceformed by drops of water in a first number of sizes. Also, piezoelectricsensor 300 may be configured to detect ice formed by drops of waterhaving a second number of sizes. In these illustrative examples, thefirst number of sizes is smaller than the second number of sizes. Thedifferent conditions may be detected based on placement of piezoelectricsensor 300 on aircraft 100 in FIG. 1.

For example, the first number of sizes may be from about 0.00465millimeters in diameter to about 0.111 millimeters in diameter. Thesecond number of sizes may be from about 0.112 millimeters to about 2.2millimeters in diameter.

The second number of sizes of the drops of water may be drops of waterthat are considered to be drops of supercooled water. Thus, these dropsof supercooled water may be supercooled large drops.

Vibrations 312 may change when ice 316 is on surface 318 ofpiezoelectric material 304. In these depicted examples, surface 318 isexposed to the external environment. In this illustrative example,changes in vibrations 312 are different with ice 316 on surface 318 asopposed to when ice 316 is absent from surface 318. Further, changes invibrations 312 are different when liquid 320 is present on surface 318.In other words, the changes in vibrations 312 may be used to distinguishbetween a presence of liquid 320 or ice 316 on surface 318 ofpiezoelectric material 304.

In these illustrative examples, vibrations 313 do not change in responseto ice 316 being present. Piezoelectric material 305 is not exposed tothe exterior of the aircraft in a manner that allows for the formationof ice 316 on piezoelectric material 305. However, piezoelectricmaterial 305 may be exposed to the same temperatures as piezoelectricmaterial 304.

This exposure to temperatures may be such that changes in temperatureresult in vibrations 312 in piezoelectric material 304 and vibrations313 in piezoelectric material 305 being substantially the same oridentical when ice 316 or other fluid is not present on surface 318 ofpiezoelectric material 304. In other words, vibrations 313 inpiezoelectric material 305 are reference vibrations for vibrations 312in piezoelectric material 304.

Vibration detector 308 is hardware and may include software. Vibrationdetector 308 is configured to detect vibrations 312 and generate datapacket 324. Data packet 324 is an example of a data packet that may bein data 222 in FIG. 2. Data packet 324 may be used to determine whetherice 316 is present on surface 318 of piezoelectric material 304.

In still other illustrative examples, data packet 324 also may be usedto determine mass 326 of ice 316 on surface 318 of piezoelectricmaterial 304. For example, the measurement of the frequency shift inpiezoelectric material 304 from a designated baseline frequency forpiezoelectric material 304 may be used to determine mass 326 of ice 316on surface 318 of piezoelectric material 304.

In these illustrative examples, temperature sensor 307 is a hardwaredevice configured to monitor the temperature of crystals 310 inpiezoelectric material 304. Temperature sensor 307 may be, for example,without limitation, a thermistor, a pyrometer, or some other suitabletype of temperature sensor to monitor the temperature of crystals 310.In other illustrative examples, temperature sensor 307 may be absent.Temperature sensor 307 also may be used to determine whether thetemperature is low enough to cause liquid 320, such as water droplets,to form ice 316.

Heater 309 is a hardware device configured to remove ice 316 fromsurface 318 of piezoelectric material 304. Heater 309 is an example of adevice that may be implemented in anti-icing system 230 in FIG. 2. Asdepicted, heater 309 may be implemented using an electrical resistiveheater, a flash heater, or some other suitable type of device.

Removing ice 316 from surface 318 of piezoelectric material 304 allowsthe detection of future formation of ice 316 on surface 318 ofpiezoelectric material 304. The removal of ice 316 from surface 318 ofpiezoelectric material 304 may occur after ice 316 has been removed fromother portions of surface 210 of vehicle 202.

Turning now to FIG. 4, an illustration of a block diagram of a datapacket that may be generated by a piezoelectric sensor is depicted inaccordance with an illustrative embodiment. In this figure, examples ofdata that may be included in data packet 324 and generated by vibrationdetector 308 are shown. As depicted, data packet 324 includes frequency400, difference 402, sensor identifier 404, and timestamp 406.

Frequency 400 is the frequency of vibrations 312 in piezoelectricmaterial 304. Difference 402 identifies the difference between frequency400 of vibration 312 in piezoelectric material 304 and the frequency ofvibrations 313 in piezoelectric material 305.

Sensor identifier 404 is a unique identifier identifying thepiezoelectric sensor generating data packet 324. Timestamp 406identifies the time when the data in data packet 324 was generated.

The illustration of icing condition detection environment 200 in FIG. 2and the different components in FIG. 3 and FIG. 4 are not meant to implyphysical or architectural limitations to the manner in which anillustrative embodiment may be implemented.

For example, in some illustrative examples, piezoelectric material 305may be omitted. The expected frequency of vibrations 312 when ice 316 ispresent on surface 318 of piezoelectric material 304 may be stored in adatabase. The database may provide expected frequencies for theformation of ice 316 at different temperatures and altitudes.

In another illustrative example, data packet 324 may include other typesof information in addition to or in place of the information illustratedin FIG. 4. For example, in some illustrative examples, data packet 324also may include an identification of a temperature. The temperature maybe used to determine whether frequency 400 indicates a presence of icewhen difference 402 is not included in data packet 324.

Turning now to FIG. 5, an illustration of a piezoelectric sensor isdepicted in accordance with an illustrative embodiment. Piezoelectricsensor 500 is an example of a physical implementation of piezoelectricsensor 300 shown in block form in FIG. 3.

Piezoelectric sensor 500 includes housing 502. Housing 502 is designedto fit within opening 504 in surface 126 of fuselage 106 in FIG. 1.Housing 502 is configured to have a shape that is substantially flush tosurface 126 when placed into opening 504. Further, the shape of housing502 is such that housing 502 substantially conforms to curvature 506 insurface 126.

Additionally, housing 502 also has opening 508. Opening 508 has asubstantially circular shape in this illustrative example. Of course,opening 508 may have any shape desired depending on the particularimplementation. Opening 508 exposes surface 510 of piezoelectricmaterial 512 located in housing 502 of piezoelectric sensor 500.

Turning now to FIG. 6, an illustration of a cross-sectional view of apiezoelectric sensor installed in an aircraft fuselage is depicted inaccordance with an illustrative embodiment. In this illustrativeexample, a cross-sectional view of piezoelectric sensor 500 is seentaken along lines 6-6 in FIG. 5.

In this view, housing 502 is depicted such that at least one of surface600 of housing 502 and surface 510 of piezoelectric material 512 issubstantially flush to surface 126. In particular, surface 600 ofhousing 502 and surface 510 of piezoelectric material 512 may havecurvature 506 such that surface 600 of housing 502 and surface 510 ofpiezoelectric material 512 substantially conform to curvature 506 ofsurface 126 of aircraft 100.

In this view, vibration generator 602 and vibration detector 604 alsoare seen within housing 502. These components are implemented usingintegrated circuits in these illustrative examples.

The different components shown in FIG. 1 and FIGS. 4-6 may be combinedwith components in FIGS. 2-3, used with components in FIG. 2-3, or acombination of the two. Additionally, some of the components in FIG. 1and FIGS. 4-6 may be illustrative examples of how components shown inblock form in FIGS. 2-3 can be implemented as physical structures.

With reference now to FIG. 7, an illustration of a flowchart of aprocess for detecting an icing condition is depicted in accordance withan illustrative embodiment. The process illustrated in FIG. 7 may beimplemented in icing condition detection environment 200 in FIG. 2. Inparticular, the different operations may be implemented within icingcondition detection system 204.

The process begins by causing vibrations in a piezoelectric materialassociated with a surface of a vehicle (operation 700). In thisillustrative example, the vibrations may be vibrations in a shear mode.The process then determines whether an icing condition is present on thepiezoelectric material from the vibrations (operation 702). The icingcondition may be ice, water droplets that may form ice, or both ice andwater droplets in these illustrative examples.

If it is determined that an icing condition is present on thepiezoelectric material, an operation is initiated (operation 704) withthe process returning to operation 700. This operation may include, forexample, without limitation, generating an alert, initiating operationof an anti-icing system, and other suitable operations. The alert maybe, for example, a visual alert, an audio alert, or both a visual alertand an audio alert that are presented to an operator of the vehicle.

In other illustrative examples, operation 704 may be the initiation ofan anti-icing system. With the initiation of the anti-icing system, icethat has accumulated on the surface of the piezoelectric material may beremoved. With reference again to operation 702, if it is determined thatan icing condition is absent, the process returns to operation 700 asdescribed above.

Turning now to FIG. 8, an illustration of a flowchart of a process fordetecting vibrations in a piezoelectric sensor is depicted in accordancewith an illustrative embodiment. The process illustrated in FIG. 8 maybe implemented in a piezoelectric sensor in number of piezoelectricsensors 208 in icing condition detection system 204 in FIG. 2. Inparticular, this process may be implemented in vibration detector 308 inpiezoelectric sensor 300 in FIG. 3.

The process begins by identifying a frequency of vibrations in apiezoelectric material in a piezoelectric sensor (operation 800). Inoperation 800, the piezoelectric material is a piezoelectric materialthat is exposed to the environment around the vehicle. In other words,the exposure is such that if ice forms on the surface of the vehicle,ice may also form on the piezoelectric material.

Next, a data packet is generated using the detected frequency (operation802). The data packet may also include an identification of thepiezoelectric sensor, a timestamp, and other suitable information. Forexample, a frequency of another piezoelectric material in thepiezoelectric sensor that is not exposed to the environment may also beidentified and included in the data packet. Additionally, the datapacket may also include multiple frequencies, amplitudes, and phases forthe piezoelectric material in the piezoelectric sensor.

The process then sends the data packet to a controller (operation 804).The process then returns to operation 800 as described above.

Turning now to FIG. 9, an illustration of a flowchart of a process fordetermining whether an icing condition is present is depicted inaccordance with an illustrative embodiment. The process illustrated inFIG. 9 is an example of an implementation for operation 702 in FIG. 7.The different operations in this flowchart may be performed bycontroller 218 in icing condition detection system 204 in FIG. 2.

The process begins by receiving a data packet from a piezoelectricsensor (operation 900). The piezoelectric sensor sending the data packetis identified from a sensor identifier in the data packet. Frequenciesof vibrations identified in the data packet are analyzed to determinewhether an icing condition is present on the piezoelectric sensor(operation 902). In operation 902, the analysis may determine how muchice or water droplets are present in addition to whether an icingcondition is present.

Further, in these illustrative examples, the frequencies may be analyzedin a manner that distinguishes between a presence of ice and a liquidsuch as water. The formation of ice on the surface of the piezoelectricsensor may result in a greater reduction in frequency than when a liquidis present on the surface of the piezoelectric sensor.

Next, the process stores the frequencies of the vibrations inassociation with the piezoelectric sensor (operation 904) with theprocess returning to operation 900 as described above. In this manner, ahistory of frequencies may be collected for use in determining whetherice is present on the piezoelectric sensor when the analysis isperformed in operation 902.

Further, this history of frequencies may be used to determine whetherdifferent types of icing conditions are present on the surface of thepiezoelectric sensor. For example, the icing rate, the presence ofmeasurable individual frequency changes, and other factors may indicatethe presence of supercooled large drop icing conditions on the surfaceof the piezoelectric sensor.

Additionally, as an operation is initiated in operation 704, such as theanti-icing system, more data is added to the history of frequencies. Inother words, as the anti-icing system thaws the ice on the surface ofthe piezoelectric sensor and the ice cools again, the measured frequencychanges may help determine which type of icing condition is present onthe surface of the piezoelectric sensor. For example, with supercooledlarge drop icing conditions, the frequency changes will be much largerthan the frequency changes during normal icing conditions.

The flowcharts and block diagrams in the different depicted embodimentsillustrate the architecture, functionality, and operation of somepossible implementations of apparatuses and methods in an illustrativeembodiment. In this regard, each block in the flowcharts or blockdiagrams may represent a module, segment, function, and/or a portion ofan operation or step. For example, one or more of the blocks may beimplemented as program code, in hardware, or a combination of theprogram code and hardware. When implemented in hardware, the hardwaremay, for example, take the form of integrated circuits that aremanufactured or configured to perform one or more operations in theflowcharts or block diagrams.

In some alternative implementations of an illustrative embodiment, thefunction or functions noted in the blocks may occur out of the ordernoted in the figures. For example, in some cases, two blocks shown insuccession may be executed substantially concurrently, or the blocks maysometimes be performed in the reverse order, depending upon thefunctionality involved. Also, other blocks may be added in addition tothe illustrated blocks in a flowchart or block diagram.

Turning now to FIG. 10, an illustration of a data processing system isdepicted in accordance with an illustrative embodiment. Data processingsystem 1000 may be used to implement computer system 226 in FIG. 2. Inthis illustrative example, data processing system 1000 includescommunications framework 1002, which provides communications betweenprocessor unit 1004, memory 1006, persistent storage 1008,communications unit 1010, input/output (I/O) unit 1012, and display1014. In this example, communication framework may take the form of abus system.

Processor unit 1004 serves to execute instructions for software that maybe loaded into memory 1006. Processor unit 1004 may be a number ofprocessors, a multi-processor core, or some other type of processor,depending on the particular implementation.

Memory 1006 and persistent storage 1008 are examples of storage devices1016. A storage device is any piece of hardware that is capable ofstoring information, such as, for example, without limitation, data,program code in functional form, and/or other suitable informationeither on a temporary basis and/or a permanent basis. Storage devices1016 may also be referred to as computer readable storage devices inthese illustrative examples. Memory 1006, in these examples, may be, forexample, a random access memory or any other suitable volatile ornon-volatile storage device. Persistent storage 1008 may take variousforms, depending on the particular implementation.

For example, persistent storage 1008 may contain one or more componentsor devices. For example, persistent storage 1008 may be a hard drive, aflash memory, a rewritable optical disk, a rewritable magnetic tape, orsome combination of the above. The media used by persistent storage 1008also may be removable. For example, a removable hard drive may be usedfor persistent storage 1008.

Communications unit 1010, in these illustrative examples, provides forcommunications with other data processing systems or devices. In theseillustrative examples, communications unit 1010 is a network interfacecard.

Input/output unit 1012 allows for input and output of data with otherdevices that may be connected to data processing system 1000. Forexample, input/output unit 1012 may provide a connection for user inputthrough a keyboard, a mouse, and/or some other suitable input device.Further, input/output unit 1012 may send output to a printer. Display1014 provides a mechanism to display information to a user.

Instructions for the operating system, applications, and/or programs maybe located in storage devices 1016, which are in communication withprocessor unit 1004 through communications framework 1002. The processesof the different embodiments may be performed by processor unit 1004using computer-implemented instructions, which may be located in amemory, such as memory 1006.

These instructions are referred to as program code, computer usableprogram code, or computer readable program code that may be read andexecuted by a processor in processor unit 1004. The program code in thedifferent embodiments may be embodied on different physical or computerreadable storage media, such as memory 1006 or persistent storage 1008.

Program code 1018 is located in a functional form on computer readablemedia 1020 that is selectively removable and may be loaded onto ortransferred to data processing system 1000 for execution by processorunit 1004. Program code 1018 and computer readable media 1020 formcomputer program product 1022 in these illustrative examples. In oneexample, computer readable media 1020 may be computer readable storagemedia 1024 or computer readable signal media 1026. In these illustrativeexamples, computer readable storage media 1024 is a physical or tangiblestorage device used to store program code 1018 rather than a medium thatpropagates or transmits program code 1018.

Alternatively, program code 1018 may be transferred to data processingsystem 1000 using computer readable signal media 1026. Computer readablesignal media 1026 may be, for example, a propagated data signalcontaining program code 1018. For example, computer readable signalmedia 1026 may be an electromagnetic signal, an optical signal, and/orany other suitable type of signal. These signals may be transmitted overcommunications links, such as wireless communications links, opticalfiber cable, coaxial cable, a wire, and/or any other suitable type ofcommunications link.

The different components illustrated for data processing system 1000 arenot meant to provide architectural limitations to the manner in whichdifferent embodiments may be implemented. The different illustrativeembodiments may be implemented in a data processing system includingcomponents in addition to and/or in place of those illustrated for dataprocessing system 1000. Other components shown in FIG. 10 can be variedfrom the illustrative examples shown. The different embodiments may beimplemented using any hardware device or system capable of runningprogram code 1018.

Illustrative embodiments of the disclosure may be described in thecontext of aircraft manufacturing and service method 1100 as shown inFIG. 11 and aircraft 1200 as shown in FIG. 12. Turning first to FIG. 11,an illustration of an aircraft manufacturing and service method isdepicted in accordance with an illustrative embodiment. Duringpre-production, aircraft manufacturing and service method 1100 mayinclude specification and design 1102 of aircraft 1200 in FIG. 12 andmaterial procurement 1104.

During production, component and subassembly manufacturing 1106 andsystem integration 1108 of aircraft 1200 in FIG. 12 takes place.Thereafter, aircraft 1200 in FIG. 12 may go through certification anddelivery 1110 in order to be placed in service 1112. While in service1112 by a customer, aircraft 1200 in FIG. 12 is scheduled for routinemaintenance and service 1114, which may include modification,reconfiguration, refurbishment, and other maintenance or service.

Each of the processes of aircraft manufacturing and service method 1100may be performed or carried out by a system integrator, a third party,and/or an operator. In these examples, the operator may be a customer.For the purposes of this description, a system integrator may include,without limitation, any number of aircraft manufacturers andmajor-system subcontractors; a third party may include, withoutlimitation, any number of vendors, subcontractors, and suppliers; and anoperator may be an airline, a leasing company, a military entity, aservice organization, and so on.

With reference now to FIG. 12, an illustration of an aircraft isdepicted in which an illustrative embodiment may be implemented. In thisexample, aircraft 1200 is produced by aircraft manufacturing and servicemethod 1100 in FIG. 11 and may include airframe 1202 with plurality ofsystems 1204 and interior 1206. Examples of systems 1204 include one ormore of propulsion system 1208, electrical system 1210, hydraulic system1212, and environmental system 1214. Any number of other systems may beincluded. Although an aerospace example is shown, different illustrativeembodiments may be applied to other industries, such as the automotiveindustry.

Apparatuses and methods embodied herein may be employed during at leastone of the stages of aircraft manufacturing and service method 1100 inFIG. 11. For example, number of piezoelectric sensors 208 in icingcondition detection system 204 may be installed in aircraft 1200 duringsystem integration 1108. These sensors also may be installed duringmaintenance and service 1114 as an upgrade or refurbishment of aircraft1200.

Thus, the illustrative embodiments provide a method and apparatus fordetecting a presence of one or more icing conditions on an aircraft aswell as other vehicles. In these illustrative examples, the actualpresence of an icing condition may be detected as well as the mass ofthe ice or water droplets that form on the piezoelectric sensors. Withthe use of piezoelectric sensors, false indications of ice on thesurface of an aircraft may be reduced. Further, the illustrativeembodiments may detect different types of icing conditions present onthe surface of the aircraft or other vehicles.

The description of the different illustrative embodiments has beenpresented for purposes of illustration and description, and is notintended to be exhaustive or limited to the embodiments in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. For example, although the illustrativeexamples for an illustrative embodiment are described with respect to anaircraft, an illustrative embodiment may be applied to other vehiclesother than aircraft. Other vehicles may include, for example, withoutlimitation, a submarine, a personnel carrier, a tank, a train, anautomobile, a bus, a spacecraft, a surface ship, and other suitablevehicles.

Further, different illustrative embodiments may provide differentfeatures as compared to other illustrative embodiments. The embodimentor embodiments selected are chosen and described in order to bestexplain the principles of the embodiments, the practical application,and to enable others of ordinary skill in the art to understand thedisclosure for various embodiments with various modifications as aresuited to the particular use contemplated.

What is claimed is:
 1. An apparatus comprising: a first piezoelectricmaterial having a first surface proximate to a surface of a vehicle andconfigured to vibrate in a shear mode wherein the first piezoelectricmaterial vibrates in a direction perpendicular to a direction in whichwaves generated by the first piezoelectric material propagate; a secondpiezoelectric material having a second surface remote from the surfaceof the vehicle and configured to vibrate in the shear mode; a vibrationdetector configured to detect a difference in a frequency of vibrationsin the first piezoelectric material compared to a frequency ofvibrations in the second piezoelectric material to detect a presence ofan icing condition on the first surface of the first piezoelectricmaterial; and an electrical resistive heater configured to remove icefrom the surface of the vehicle.
 2. The apparatus of claim 1, whereinthe first piezoelectric material and the vibration detector form apiezoelectric sensor.
 3. The apparatus of claim 1 further comprising: avibration generator configured to cause the first piezoelectric materialto vibrate.
 4. The apparatus of claim 1, wherein the first piezoelectricmaterial and the vibration detector are associated with a housinginstalled in the vehicle such that the first surface of the firstpiezoelectric material is flush with the surface of the vehicle.
 5. Theapparatus of claim 1, wherein in being configured to detect thedifference in the frequency of vibrations in the first piezoelectricmaterial that indicates the presence of the icing condition on thesurface of the first piezoelectric material, the vibration detector isconfigured to detect a number of icing conditions on the surface of thefirst piezoelectric material based on a change in the vibrations.
 6. Theapparatus of claim 1 further comprising: an anti-icing system configuredto remove ice from the first surface of the first piezoelectricmaterial.
 7. The apparatus of claim 1, wherein: the first surface of thefirst piezoelectric material is exposed to an environment; the secondsurface of the second piezoelectric material is not exposed to theenvironment; and the second piezoelectric material is identical to thefirst piezoelectric material.
 8. The apparatus of claim 7, wherein thefirst piezoelectric material and the second piezoelectric material areexposed to a same temperature, wherein changes in the temperature resultin vibrations in the first piezoelectric material being the same as thevibrations in the second piezoelectric material when ice or other fluidis not present on the surface of the first piezoelectric material, andwherein the vibration detector is further configured to detect a changein the frequency of vibration of the first piezoelectric materialrelative to a frequency of vibration of the second piezoelectricmaterial to indicate the presence of the icing condition on the surfaceof the first piezoelectric material.
 9. The apparatus of claim 1,wherein the icing condition is selected from at least one of ice on thesurface of the vehicle and water droplets on the surface of the vehiclein conditions that cause the water droplets to form the ice.
 10. Anapparatus comprising: a first piezoelectric material having a firstsurface proximate to a surface of a vehicle and configured to vibrate ina shear mode wherein the piezoelectric material vibrates in a directionperpendicular to a direction in which waves generated by the firstpiezoelectric material propagate; a second piezoelectric material havinga second surface remote from the surface of the vehicle and configuredto vibrate in the shear mode; a vibration detector configured to detecta difference in vibrations in a frequency of vibration of the firstpiezoelectric material compared to a frequency of vibration of thesecond piezoelectric material to indicate a presence of ice on the firstsurface of the first piezoelectric material; and an electrical resistiveheater configured to remove the ice from the surface of the vehicle. 11.An apparatus comprising: a first piezoelectric material having a firstsurface proximate to a surface of a vehicle such that the first surfaceis exposed to an environment, wherein the first piezoelectric materialis configured to vibrate in a shear mode wherein the first piezoelectricmaterial vibrates in a direction perpendicular to a direction in whichwaves generated by the first piezoelectric material propagate; a secondpiezoelectric material having a second surface remote from the surfaceof the vehicle, wherein the second piezoelectric material is configuredto vibrate in the shear mode at a second frequency; a vibrationgenerator configured to detect a difference in the first frequency andthe second frequency to indicate a presence of an icing condition on thefirst surface of the first piezoelectric material; and an electricalresistive heater configured to remove ice from the surface of thevehicle.
 12. The apparatus of claim 11, wherein the first piezoelectricmaterial and the second piezoelectric material are exposed to a sametemperature.
 13. The apparatus of claim 11, wherein the vibrations inthe second piezoelectric material define reference vibrations.
 14. Theapparatus of claim 11, wherein the icing condition is selected from atleast one of ice on the surface of the vehicle and water droplets on thesurface of the vehicle in conditions that cause the water droplets toform the ice.
 15. The apparatus of claim 14, wherein the icing conditioncomprises the ice on the surface of the vehicle and the vibrationgenerator is further configured to determine an amount of the icedeveloped on the surface of the vehicle.
 16. The apparatus of claim 11,wherein the first piezoelectric material is the same as the secondpiezoelectric material.
 17. The apparatus of claim 11, wherein the firstpiezoelectric material and the second piezoelectric material areassociated with a housing installed on the vehicle such that the firstsurface of the first piezoelectric material is flush with a surface ofthe vehicle and the second surface of the second piezoelectric materialis recessed within the housing.
 18. The apparatus of claim 11, whereinthe first piezoelectric material vibrates in the shear mode such thatthe first piezoelectric material vibrates in a direction perpendicularto a direction in which waves generated by the first piezoelectricmaterial propagate.